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A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel

Description: Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowa… more
Date: January 21, 1953
Creator: Johnson, Joseph L., Jr.
Item Type: Refine your search to only Report
open access

Turbine Failure Investigation of J65-W-4 Turbojet Engine in an Altitude Test Chamber

Description: Memorandum presenting an altitude investigation to determine the basic mechanism by which J65-W-4 turbine rotor-blade failures were occurring in service. The engine was installed in an altitude test chamber and a series of controlled engine throttle bursts, with and without inlet-air distortion, over a range of altitudes, flight Mach numbers, and inlet-air temperatures. An examination of the data obtained during the investigation indicated that the danger of turbine failure could be eliminated … more
Date: September 21, 1956
Creator: McAulay, John E.; Braithwaite, Willis M. & Ciepluch, Carl C.
Item Type: Refine your search to only Report
open access

Modified tubular combustor as high-temperature gas generators

Description: A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.
Date: October 21, 1955
Creator: Friedman, Robert & Zettle, Eugene V.
Item Type: Refine your search to only Report
open access

Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines

Description: Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.
Date: April 21, 1955
Creator: Dugan, James F., Jr.
Item Type: Refine your search to only Report
open access

Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees

Description: A flight investigation was made at altitudes of 40,000, 25,000 and 15,000 feet to determine the horizontal-tail loads of the Bell X-5 research airplane at a sweep angle of 58.7 deg over the lift range of the airplane for Mach numbers from 0.61 to 1.00. The horizontal-tail loads were found to be nonlinear with lift throughout the lift ranges tested at all Mach numbers except at a Mach number of 1.00. The balancing tail loads reflected the changes which occur in the wing characteristics with inc… more
Date: July 21, 1955
Creator: Reed, Robert D.
Item Type: Refine your search to only Report
open access

The effect of fluid injection on the compressible turbulent boundary layer: preliminary tests on transpiration cooling of a flat plate at M = 2.7 with air as the injected gas

Description: Report presenting local values of heat-transfer rate and temperature-recovery factor obtained on a transpiration-cooled flat plate. The results show primarily that transpiration cooling in a turbulent boundary layer at M = 2.7 has marked effects on the heat transfer and recovery temperature for nearly uniform air injection along the plate.
Date: December 21, 1955
Creator: Rubesin, Morris W.; Pappas, Constantine C. & Okuno, Arthur F.
Item Type: Refine your search to only Report
open access

Evaporation of JP-5 fuel sprays in air streams

Description: Report presenting a continuous sampling-probe technique used to determine the percentage of JP-5 fuel spray evaporated under conditions common in ramjet engines. Fuel was injected contraststream from a multiple-orifice injector and sampling data were obtained at several distances downstream of the injector. An expression is generated for a description of this phenomenon.
Date: February 21, 1956
Creator: Foster, Hampton H. & Ingebo, Robert D.
Item Type: Refine your search to only Report
open access

Investigation of Interference Lift, Drag, and Pitching Moment of a Series of Triangular-Wing and Body Combinations at a Mach Number of 1.94

Description: Report presenting an investigation at Mach number 1.94 of a series of triangular-wing and body combinations to determine the interference lift, drag, and pitching moment. The models had a series of seven flat-plate triangular wings of varying scale, four with semiapex angles of 30 degrees, and three with semiapex angles of 45 degrees. Results indicated that the interference between the wing and the body gave an increase in lift over the wing and body alone, but at the expense of more drag.
Date: December 21, 1955
Creator: Coletti, Donald E.
Item Type: Refine your search to only Report
open access

A Theoretical Investigation of a Compensating Network With Application to Roll Control Systems for Automatic Interceptors

Description: Memorandum presenting a theoretical analysis of an airplane automatic control system incorporating a compensating network. The compensating network is a computing network that has characteristics that are the inverse of the airframe; consequently, airplane dynamics are eliminated from the system response. Results regarding the displacement control system, the velocity command system, and the acceleration control system are provided.
Date: July 21, 1955
Creator: Sherman, Windsor L.
Item Type: Refine your search to only Report
open access

An experimental investigation at a Mach number of 2.01 of the effects of body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies of a given length and volume but various cross-section shapes were tested at a Mach number of 2.01. The results showed that changes in drag at zero lift due to changes in body cross-section shape from the basic circular shape are small and of the same order a… more
Date: July 21, 1955
Creator: Carlson, Harry W. & Gapcynski, John P.
Item Type: Refine your search to only Report
open access

Load distributions on wings and wing-body combinations at high angles of attack and supersonic speeds

Description: Report presenting an investigation of aircraft which are required to maneuver rapidly at extreme altitudes, which involves reaching maximum loads at high angles of attack. Load information is necessary for that flight condition and for aircraft that reach their maximum loads at high speed and high dynamic pressures. Results regarding the wings and wing-body combinations are provided.
Date: July 21, 1955
Creator: Katzen, Elliott D. & Pitts, William C.
Item Type: Refine your search to only Report
open access

Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Longitudinal Stability and Control of the Model Equipped with a Supersonic-Type Elliptical Wing-Root Inlet

Description: Memorandum presenting development tests on a 1/4-scale model of the Republic F-105 airplane in the 19-foot pressure tunnel. The tests in this particular report include longitudinal stability and control tests of the basic design provided by the contractor, tests of various modifications designed to improve the stability characteristics of the model with the trailing-edge flaps deflected, brief exploratory lateral-control and rudder-effectiveness tests, and stall studies and duct air-flow measur… more
Date: July 21, 1954
Creator: Kelly, H. Neale & Cancro, Patrick A.
Item Type: Refine your search to only Report
open access

A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds

Description: Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date: July 21, 1958
Creator: Heath, Atwood R., Jr. & Igoe, Ann W.
Item Type: Refine your search to only Report
open access

An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds

Description: Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date: August 21, 1953
Creator: Henry, Beverly Z., Jr. & Braden, John A.
Item Type: Refine your search to only Report
open access

Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback-Wing Airplane Model With Various Vertical Locations of Wing and Horizontal Tail: Static Longitudinal Stability and Control, M = 2.01

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch and of a supersonic airplane configuration at Mach number 2.01. The model was equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The configurations investigated included a high-wing, a mid-wing, and a low-wing arrangement, each with fo… more
Date: February 21, 1956
Creator: Spearman, M. Leroy & Driver, Cornelius
Item Type: Refine your search to only Report
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor ratio and low compressor-tip speed 5: experimental performance of two-stage turbine with downstream stator

Description: An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.
Date: October 21, 1951
Creator: Davison, Elmer H.; Petrash, Donald A. & Schum, Harold J.
Item Type: Refine your search to only Report
open access

Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations

Description: Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.
Date: July 21, 1958
Creator: Penland, Jim A. & Armstrong, William O.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation of the Effect of Spin on the Aerodynamic Characteristics of a 60-Millimeter T-24 Mortar Shell With Several Tail-Fin Configurations

Description: Report discussing an investigation to determine the effect of spin on the aerodynamic characteristics of the Army Ordnance Corps 60-millimeter T-24 mortar shell with several tail-fin configurations. Tests were performed at several airspeeds, speeds of rotation, and angles of attack. Under all test conditions, the models were statistically stable and the yawing moment increased with speed of rotation at higher angles of attack.
Date: March 21, 1957
Creator: Kemp, William B., Jr. & Hayes, William C., Jr.
Item Type: Refine your search to only Report
open access

Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results

Description: "A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases" (p. 1).
Date: May 21, 1952
Creator: Scadron, Marvin D.
Item Type: Refine your search to only Report
open access

Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01

Description: Memorandum presenting an investigation in the supersonic pressure tunnel at a free-stream Mach number of 2.01 and at angles of attack up to 15 degrees of the static pressures and boundary-layer characteristics on the forward parts of nine fusleages of various cross-sectional shapes. Results regarding the static pressure distributions, boundary-layer characteristics, and selection of fuselage shapes for use with top-mounted scoop inlets are provided.
Date: January 21, 1957
Creator: Hasel, Lowell E. & Kouyoumjian, Walter L.
Item Type: Refine your search to only Report
open access

Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests

Description: Memorandum presenting the buffet characteristics of a scale model of an attack airplane over a range of Mach numbers. The wing had a modified delta plan form with an NACA 0008 airfoil section at the root and an NACA 0005 airfoil section at the tip, a leading-edge sweep of 41.11 degrees, an aspect ratio of 2.91, and a taper ratio of 0.226. Results regarding the frequency spectrum of bending moment, effect of density on root-mean-square bending moment, system damping coefficients, and buffet inpu… more
Date: February 21, 1958
Creator: Davis, Don D., Jr. & Wornom, Dewey E.
Item Type: Refine your search to only Report
open access

Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets

Description: "The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).
Date: October 21, 1957
Creator: Hearth, Donald P.; Anderson, Bernhard H. & Dryer, Murray
Item Type: Refine your search to only Report
open access

Performance of Twin-Duct Variable-Geometry Side Inlets at Mach Numbers of 1.5 to 2.0

Description: Report presenting testing of the performance of a twin-duct air-intake system mounted on the sides of a 1/8-scale fuselage forebody model of a proposed aircraft at several Mach numbers, angles of attack, and yaw. Results regarding the inlet survey, compression-surface boundary-layer removal and effects of second-ramp position, instability, effect of cant on inlet performance, inlet performance with 0 and 30 degree second ramp angles, performance with fixed second-ramp angles, and effect of cana… more
Date: January 21, 1957
Creator: Yeager, Richard A.; Beheim, Milton A. & Klann, John L.
Item Type: Refine your search to only Report
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